EP1485288B1 - Systeme d'actionnement pour une helice a pas reglable - Google Patents

Systeme d'actionnement pour une helice a pas reglable Download PDF

Info

Publication number
EP1485288B1
EP1485288B1 EP03716179A EP03716179A EP1485288B1 EP 1485288 B1 EP1485288 B1 EP 1485288B1 EP 03716179 A EP03716179 A EP 03716179A EP 03716179 A EP03716179 A EP 03716179A EP 1485288 B1 EP1485288 B1 EP 1485288B1
Authority
EP
European Patent Office
Prior art keywords
pitch
pitch change
valve
pressure
propeller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP03716179A
Other languages
German (de)
English (en)
Other versions
EP1485288A1 (fr
Inventor
David V. Arel
Robert Perkinson
David Danielson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hamilton Sundstrand Corp
Original Assignee
Hamilton Sundstrand Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hamilton Sundstrand Corp filed Critical Hamilton Sundstrand Corp
Publication of EP1485288A1 publication Critical patent/EP1485288A1/fr
Application granted granted Critical
Publication of EP1485288B1 publication Critical patent/EP1485288B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H3/00—Propeller-blade pitch changing
    • B63H3/06—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical
    • B63H3/08—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid
    • B63H3/081—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid actuated by control element coaxial with the propeller shaft
    • B63H3/082—Propeller-blade pitch changing characterised by use of non-mechanical actuating means, e.g. electrical fluid actuated by control element coaxial with the propeller shaft the control element being axially reciprocatable

Definitions

  • the present invention relates to a propeller control system, and more particularly to an electronic/hydraulic control system for propeller blade angle control which minimizes the number of pressures which pass through a transfer bearing.
  • Common variable pitch propeller systems are actuated through metered hydraulic pressures generated in the stationary field of the engine and transferred into the rotational field of the propeller blades through a transfer bearing.
  • hydraulic pressures required to adjust propeller blade pitch angle are supplied directly from the transfer bearing to a coarse pitch and a fine pitch chamber of the pitch change actuator to provide propeller pitch control.
  • a multiple of additional pressures are also supplied through the transfer bearing to assure backup and feathering pressures which protect the propeller system against uncommanded blade angle excursions. Each of these pressures are separately communicated through the transfer bearing.
  • the transfer bearing must communicate the multiple of pressures from the stationary field to the rotational field while minimizing leakage.
  • the conventional transfer bearing supplies appropriately metered hydraulic pressure directly to each particular propeller pitch change system, any leakage may degrade the accuracy of the pitch change system.
  • Conventional transfer bearings are therefore relatively complicated and critical systems. Moreover, the greater the number of pressures which must pass through the transfer bearing, the greater the complexity and expense thereof.
  • US 5037271 describes a pitch control system which employs both an electrical control and a mechanical back-up control for controlling propeller pitch. In the event of electrical control failure, the system switches to mechanical control.
  • US 2995190 describes a mechanical pitch control system which employs a pitch limiting means to limit the pitch movements under certain operating conditions.
  • GB 2347974 describes a pitch control system in which a pitch control valve is controlled via two hydraulic connections during normal operation, or through application of a protect pressure, can switch the system to a manual override or back-up system.
  • EP 0387183 describes a propeller control system comprising a propeller shaft which rotates about a first axis to drive a propeller hub and a plurality of propeller blades extending therefrom, a pitch change valve mounted along said first axis, said pitch change valve movable along said axis, axial movement of said pitch change valve operable to change a pitch of said plurality of propeller blades, and a transfer bearing comprising a single land for supplying a supply pressure from a stationary field to said pitch change valve within a rotational field.
  • the present invention is characterised in that the pitch change valve is in a hydraulic balance and is movable along said axis in response to upset of said hydraulic balance, and in that said supply pressure is operable to maintain said hydraulic balance.
  • the propeller control system provides for actuation through a supply pressure only.
  • a transfer bearing thereby requires only a single land to provide supply pressure into the system for actuation and control.
  • the supply pressure is metered at a pitch change valve within the rotating propeller shaft downstream of the transfer bearing. As the transfer bearing is upstream of the pitch change valve, leakage from the transfer bearing has minimal effect upon the accuracy of the system.
  • only a supply pressure is output from the main pump other pressures are provided within the pitch change valve through particular orifice and valve sizing.
  • a main pump provides supply pressure to the transfer bearing through a pressure regulating valve. From the transfer bearing, supply pressure is provided to the pitch change valve.
  • the pitch change valve translates to selectively communicate a coarse pitch change pressure and a fine pitch change pressure to supply pressure or drain pressure.
  • speed governing, synchrophasing, beta control, feathering and unfeathering of the propeller blades are provided.
  • a backup mode of moving propeller blade angle in the coarse pitch direction is provided by the present invention. Movement towards the coarse pitch direction is the 'fail-safe' action for propellers.
  • a rotating controller and/or a separate non-rotating propeller backup control commands an increase in propeller blade angle if at least any of the following conditions are detected: a) propeller overspeed condition, b) propeller blade angle below the minimum in-flight value during a flight, or c) receipt of a feather command from the cockpit.
  • the command to increase the propeller blade angle is an electrical signal that energizes a feathering solenoid. Actuation of the feathering solenoid increases the supply pressure within the system.
  • the increased supply pressure changes the hydraulic force balance of the pitch change valve to causes a feather actuating valve to move forward relative a pitch change valve sleeve until a feather override orifice between supply pressure and a Feather Override Chamber is closed.
  • the Feather Override Chamber is connected to drain pressure and the pressure within the Feather Override Chamber drops to drain pressure.
  • the balance of forces will be rapidly changed causing the Pitch Change Valve Spool to translate aft of its starting position.
  • a coarse pitch pressure metering window is opened to allow fluid at the increased supply pressure into the Coarse Pitch chamber while simultaneously opening a Fine Pitch Pressure Metering Window to allow fluid within a Fine Pitch chamber to flow to drain pressure.
  • the flow to drain changes the hydraulic balance on a Pitch Change Actuator Piston and drives a pitch link attached to each propeller blade to thereby change the pitch thereof towards coarse pitch.
  • the feather override mode will be maintained until either a) the pitch change actuator piston actuator reaches the feather position and contacts a mechanical feather stop, or b) the controller de-energizes the feathering solenoid because the hazardous condition no longer exists.
  • the present invention provides a propeller control system which minimizes the number of pressures which are communicated through a transfer bearing, assures effective protection against uncommanded blade angle excursions, and reduces the overall system size, weight, complexity and expense.
  • FIG 1 illustrates a general perspective view of a propeller control system 20 including a gas turbine engine (illustrated schematically at 22) which rotates a turbine output shaft 24 at a high speed.
  • the turbine output shaft 24 drives a gear reduction gearbox (illustrated somewhat schematically at 26) which decrease shaft rotation speed and increase output torque.
  • the gearbox 26 drives a propeller shaft 28 which rotates a. propeller hub 30 and a plurality of propeller blades 32 which extend therefrom.
  • the turbine output shaft 24 rotates in one direction while the propeller shaft 28 rotates in an opposite direction.
  • the turbine output shaft 24 and the propeller shaft 28 rotate about a common axis A.
  • Axis A is substantially perpendicular to a plane P which is defined by the propeller blades 32.
  • a permanent magnet alternator (PMA) 34 which rotates about axis A to provide electrical power directly to the rotating propeller hub 30 and blades 32.
  • PMA permanent magnet alternator
  • a main pump 36 for actuating the various mechanism disclosed herein, provides hydraulic pressure.
  • Main pump 36 provides a pressure indicated generally by the appropriately shaded areas and more specifically by the P subscript designations, wherein P s is supply pressure, and P D is drain pressure.
  • the present invention advantageously provides for actuation through supply pressure P s only.
  • a transfer bearing 38 thereby requires only a single land to provide hydraulic pressure into the system 20 for actuation and control.
  • the supply pressure P s is metered at a pitch change valve 40 (also illustrated in Figure 2B ) within the rotating propeller shaft 28 downstream of the transfer bearing 38. Hydraulic leakage is minimized which improves the pressure gain and increases accuracy of the system.
  • the transfer bearing is upstream of the pitch change valve 40, leakage from the transfer bearing 38 has minimal effect upon the accuracy of the system 20.
  • a supply pressure P s is output from the main pump 36 other pressures such as coarse pitch change pressure P c , fine pitch change pressure P f , a first metered pressure P m1 and a second metered pressure P m2 are provided within the pitch change valve 40 through particular orifice and valve sizing.
  • the main pump 36 provides fluid pressure to the transfer bearing 38 through a pressure regulating valve 42.
  • the main pump 36 provides fluid at a pressure above the supply pressure P s such that at least some fluid will circulate through the pressure regulating valve 42 and be reduced to the drain pressure P D in the drain system. Drainage from the pitch change valve 40 is communicated through the center of the pitch change valve 40 along axis A where it is communicated through the gearbox 26 ( Figure 1 ) and back into the drain system for access by the main pump 36.
  • a feathering solenoid 44 and a high pressure relief valve 46 are also preferably located between the main pump 36 and the transfer bearing 38.
  • supply pressure P s is provided to the pitch change valve 40.
  • the pitch change valve 40 translates along axis A to selectively communicate the coarse pitch change pressure P C and fine pitch change pressure P f to supply pressure P s and drain pressure P D .
  • coarse pitch change pressure P C and fine pitch change pressure P f to supply pressure P s or drain pressure P D to provide speed governing, synchrophasing, beta control, feathering and unfeathering of the propeller blades 32.
  • a pitch change actuator piston 48 is located between a coarse pitch actuator chamber PC and a fine pitch actuator chamber PF which are respectively supplied with coarse pitch change pressure P C and fine pitch change pressure P f such that the piston 48 is driven by differential pressure therebetween.
  • the pitch change actuator piston 48 translate along axis A to drive a pitch link 50 attached to each propeller blade 32 to thereby control the pitch thereof.
  • the pitch change valve 40 is axially translated in response to a pitch lock screw 52 which rotates within a threaded pitch nut 54.
  • Pitch nut 54 is mounted to the pitch change actuator piston 48 such that the pitch lock screw 52 and threaded pitch nut 54 axially slide in response to movement of the pitch change actuator piston 48.
  • a pitch change motor 56 drives the pitch lock screw 52 in response to a rotating controller 58.
  • the pitch lock screw 52 changes a hydraulic fluid balance within the pitch change valve 40 as will be further described below to provide a hydraulic servo link. That is, a pitch lock gap is maintained between the pitch lock screw 52 and the pitch changed actuator piston 48.
  • the polar moment of inertia which must be rotated by the pitch change motor 56 is minimized. This provides for improved precision for synchrophasing accuracy and dynamic response over heretofore mechanical drives.
  • the pitch lock gap is eliminated and the pitch lock screw 52 mechanically blocks movement of the pitch change actuator piston 48 to lock the propeller blades in their last pitch position.
  • the controller 58 is located within the rotational field for rotation with the propeller shaft 28.
  • a beta feedback linear variable differential transformer (LVDT 60) identifies the position of the propeller blades 32 through a mechanical linkage 62 connected to the pitch change actuating piston 48.
  • the controller 58 thereby receives a signal of actual propeller blade angle through communication with the LVDT 60.
  • controller 58 is a dual channel microprocessor based unit, having a primary channel and a backup channel, to provide closed loop control of the pitch of propeller blades 32.
  • the controller 58 functions to control speed governing, synchrophasing, beta control, feathering and unfeathering. In addition to these functions, the unit detects, isolates and accommodates control system faults.
  • the controller 58 is preferably programmed in a known manner to perform the functions as set forth above. Controller 58 drives pitch change motor 56 to drive the pitch lock screw 52 and control translation of the pitch change valve 40, described in detail below.
  • the pitch change valve 40 includes a pitch change valve spool 64, pitch change valve sleeve 66, a feather actuating valve 68, and a pitch change signal valve 70.
  • the pitch change valve sleeve 66 is axially fixed within the propeller shaft 28.
  • the pitch change valve spool 64 is axially movable along axis A relative the pitch change valve sleeve 66.
  • the pitch change valve spool 64 is biased relative the pitch change valve sleeve 66 by a spring 65 or the like.
  • the feather actuating valve 68 is biased relative the pitch change valve sleeve 66 by a spring 69 or the like.
  • the pitch change signal valve 70 is biased relative the pitch change valve sleeve 66 by a spring 71 or the like.
  • the pitch change signal valve 70 is preferably located adjacent the forward end of the pitch change valve spool 64 and opposite the feather actuating valve 68 which is located adjacent the aft end of the pitch change valve spool 64.
  • a predetermined pressures within a pitch change signal chamber 74 (first metered pressure P m1 ), a supply pressure chamber 76, and a feather override chamber 78 (second metered pressure P m2 ) maintain the pitch change valve spool 64 in a hydraulically balanced position relative the pitch change valve sleeve 66.
  • the first metered pressure P m1 and the second metered pressure P m2 are obtained from the single supply pressure P s by appropriate orifice, spring and valve sizing as generally known.
  • the pitch change lock screw 52 drives the pitch change signal valve 70 aft (toward the transfer bearing 38) relative the pitch change valve spool 64.
  • a button 73 provides a point contact between the pitch lock screw 52 and the pitch change valve sleeve 66. This movement opens a pitch change signal metering window 84 between the pitch change signal chamber 74 and drain pressure. Pressure within the pitch change signal chamber 74 decreases from the original balanced first metered pressure P m1 . This reduction of the first metered pressure P m1 changes the entire balance of forces which maintained the pitch change valve spool 64 relative the pitch change valve sleeve 66. As a result, the pitch change valve spool 64 moves aft relative the pitch change valve sleeve 66.
  • the pitch change valve spool 64 continues to moves aft until the pitch change signal metering window 84 between the pitch change signal chamber 74 and drain closes sufficiently to raise the hydraulic pressure in the pitch change signal chamber 74 to its original value. That is, the pitch change valve spool 64 moves aft until the pitch change valve spool 64 has returned to it original position relative the pitch change signal valve 70. Once the pressure returns to its original value (first metered pressure P m1 ) the balance of forces applied to the pitch change valve spool 64 is restored and movement of the pitch change valve spool 64 stops at a new position. The new position correlates to a new commanded propeller blade pitch angle.
  • a coarse pitch pressure metering window 80 located between the Pitch Change Valve Spool 64 and the Pitch Change Valve Sleeve 66 opens to allow fluid at supply pressure P s into the Coarse Pitch chamber PC.
  • a Fine Pitch Pressure Metering Window 82 opens to allow fluid within the Fine Pitch chamber PF to flow to drain pressure. This flow changes the force balance on the Pitch Change Actuator Piston 48 which translates forward along axis A to drive the pitch link 50 ( Figure 2A ) attached to each propeller blades 32 and thereby change the pitch thereof toward the desired increased (coarser) blade pitch angle.
  • the Pitch Change Lock Screw 52 moves forward along axis A away from the pitch change signal valve 70.
  • the pitch change lock screw 52 moves forward without rotating as the pitch change lock screw 52 moves with the pitch change actuator piston 48 which is connected thereto through the pitch change nut 54 ( Figure 2A ).
  • the LVDT 60 ( Figure 2A ) is also displaced through connection between the mechanical linkage 62 and the pitch change actuating piston 48.
  • the Pitch Change Signal Valve 70 moves forward, closing the Pitch Change Signal Metering Window 84 off from drain pressure.
  • the pressure within the Pitch Change Signal Chamber 74 increases as the Pitch Change Valve Spool 64 moves forward.
  • the pitch change signal metering window 84 continues to close until the pressure within the pitch change signal chamber 74 returns to the original value (first metered pressure P m1 ). This action continues until the Pitch Change Valve Spool 64 reaches a position where both the Fine Pitch metering window 82 and the Coarse Pitch Pressure Metering Window 80 are again closed (as illustrated in Figure 2B ).
  • a feather override mode is illustrated.
  • a backup mode of moving the propeller blade angle in the coarse pitch direction is provided by the present invention. Movement towards the coarse pitch direction is the 'fail-safe' direction for propellers.
  • the controller 58 and/or a separate non-rotating propeller backup control commands an increase in propeller blade angle if at least any of the following conditions are detected: a) propeller overspeed condition, b) propeller blade angle falls below the minimum in-flight value during a flight, or c) receipt of a feather command from the cockpit.
  • the command to increase the propeller blade angle is preferably an electrical signal that energizes the feathering solenoid 44.
  • Actuation of the feathering solenoid 44 will provide supply pressure to move the Pressure Regulating Valve 42 to its reset position. This increases the reference force on the Pressure Regulating Valve spring, increasing the pressure required to regulate Supply Pressure. That is, supply pressure within the system is increased as less fluid is communicated through the pressure regulating valve 42.
  • the higher Supply Pressure changes the hydraulic balance of the pitch change valve 40 and causes the Feather Actuating Valve 68 to move forward relative the pitch change valve sleeve 66, compressing spring 69, until a first feather override orifice 77 between supply pressure and the Feather Override Chamber 78 is closed. Since the Feather Override Chamber 78 ( Figure 2B ; second metered pressure P m2 ) is now connected to drain pressure (through a second feather override orifice 79), pressure in the Feather Override Chamber 78 drops to the value of drain pressure. Thus, the balance of forces on the Pitch Change Valve Spool 64 is rapidly changed causing the Pitch Change Valve Spool 64 to move aft toward the transfer bearing 38.
  • the pitch change valve spool 64 is aft of the starting position.
  • the coarse pitch pressure metering window 80 is opened to allow fluid at supply pressure into the Coarse Pitch chamber PC while simultaneously opening the Fine Pitch Pressure Metering Window 82 to allow fluid within the Fine Pitch chamber PF to flow to drain pressure.
  • the decrease to drain pressure changes the hydraulic balance on the Pitch Change Actuator Piston 48 which translates along axis A to drive the pitch link 50 ( Figure 3A ) attached to each propeller blade 32 and thereby change the pitch thereof towards coarse pitch.
  • the self-nulling features of the pitch change valve are bypassed and the pitch change actuator piston 48 moves directly toward feather.
  • the feather override mode motion will continue until either a) the pitch change actuator piston 48 reaches the feather position and contacts a mechanical feather stop, or b) the controller 58 de-energizes the Feathering solenoid 44 because the hazardous condition no longer exists. That is, the propeller blades 32 are provided with a temporary "boost" toward coarse pitch. Preferably, the controller 58 provides such a boost whenever the hazardous condition is transitory, but will allow full actuation to feather should continuous predetermined hazardous condition criterion are met.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Wind Motors (AREA)
  • Valve Device For Special Equipments (AREA)
  • Servomotors (AREA)

Abstract

L'invention concerne un système de commande d'hélice (20) permettant l'actionnement par simple pression d'acheminement. Un roulement de transfert (38) ne nécessite, de ce fait, qu'un seul appui. La pression d'acheminement est mesurée au niveau d'une valve de modification de pas (40) dans l'arbre (28) d'hélice de rotation en aval du roulement de transfert (38) afin d'exercer une pression hydraulique en vue de l'actionnement et de la commande. On obtient un mode de surpassement de flottement en énergisant un solénoïde d'oscillation (44). La pression d'acheminement accrue modifie l'équilibre de la force hydraulique de la soupape de modification du pas (40) afin de permettre à la pression d'acheminement accrue d'entrer dans une chambre de pas irrégulier et d'assurer l'écoulement simultané d'un fluide se trouvant dans la chambre à pas précis vers une pression de drain. L'écoulement vers le drain modifie l'équilibre hydraulique sur le piston actionneur de modification de pas (48) de manière à commander une liaison de pas (50) fixée à chaque lame d'hélice (32) et à modifier, par la même, le pas et obtenir un pas irrégulier.

Claims (22)

  1. Système de commande d'hélice (20) comprenant :
    un arbre d'hélice (28) qui tourne autour d'un premier axe (A) pour entraîner un moyeu d'hélice (30) et une pluralité de pales d'hélice (32) qui s'étendent de celui-ci ;
    une vanne de changement de pas (40) montée le long dudit premier axe (A), ladite vanne de changement de pas (40) étant mobile le long dudit axe (A), un mouvement axial de ladite vanne de changement de pas (40) étant opérationnel pour changer un pas de ladite pluralité de pales d'hélice (32) ; et
    un palier de transfert (38) comprenant un seul méplat pour fournir une pression d'alimentation d'un champ stationnaire à ladite vanne de changement de pas (40) dans un champ rotationnel, caractérisé en ce que ladite vanne de changement de pas est dans un équilibre hydraulique et est mobile le long dudit axe en réponse à un bouleversement dudit équilibre hydraulique, et en ce que ladite pression d'alimentation est opérationnelle pour maintenir ledit équilibre hydraulique.
  2. Système de commande d'hélice (20) selon la revendication 1, comprenant en outre un solénoïde de mise en drapeau (44) en communication avec une pompe principale (36) et ledit palier de transfert (38).
  3. Système de commande d'hélice (20) selon la revendication 2, comprenant en outre une unité de commande en communication avec ledit solénoïde de mise en drapeau (44), ladite unité de commande étant opérationnelle pour actionner et désactiver ledit solénoïde de mise en drapeau (44).
  4. Système de commande d'hélice (20) selon la revendication 3, dans lequel l'actionnement dudit solénoïde de mise en drapeau (44) augmente ladite pression d'alimentation.
  5. Système de commande d'hélice (20) selon la revendication 4, dans lequel ladite vanne de changement de pas (40) comprend une vanne de mise en drapeau (68) mobile par rapport à un tiroir de vanne de changement de pas (64), ladite vanne de mise en drapeau (68) étant mobile par rapport audit tiroir de vanne de changement de pas (64) en réponse à ladite augmentation de ladite pression d'alimentation.
  6. Système de commande d'hélice (20) selon la revendication 5, dans lequel l'actionnement de ladite vanne de mise en drapeau (68) bouleverse ledit équilibre hydraulique de ladite vanne de changement de pas (40) et change le pas de ladite pluralité de pales d'hélice (32) vers un grand pas.
  7. Système de commande d'hélice (20) selon la revendication 1, dans lequel ladite pression d'alimentation est régulée en une première pression régulée au sein d'une chambre de signal de changement de pas (74) formée entre une vanne de signal de changement de pas (70) et un tiroir de vanne de changement de pas (64) et en une seconde pression régulée au sein d'une chambre de surpassement de drapeau (78) formée entre une vanne d'actionnement de drapeau (68) et ledit tiroir de vanne de changement de pas (64).
  8. Système de commande d'hélice (20) selon la revendication 1, comprenant en outre une unité de commande (58) montée au sein du champ rotationnel.
  9. Système de commande d'hélice (20) selon la revendication 8, comprenant en outre un transformateur différentiel variable linéaire (60) en communication avec ladite unité de commande (58).
  10. Système de commande d'hélice (20) selon la revendication 9, dans lequel ledit transformateur différentiel variable linéaire (60) identifie le pas de la pluralité de pales d'hélice (32) par l'intermédiaire d'une articulation mécanique (62).
  11. Système de commande d'hélice (20) selon la revendication 10, dans lequel ladite articulation mécanique (62) est fixée sur un piston d'actionnement de changement de pas (48), ledit piston d'actionnement de changement de pas (48) étant monté de manière amovible entre une chambre d'actionneur de grand pas et une chambre d'actionneur de petit pas.
  12. Système de commande d'hélice (20) selon la revendication 1, comprenant en outre une vis de blocage de pas (52) adjacente à ladite vanne de changement de pas (40), ladite vis de blocage de pas (52) pouvant être mise en rotation par un moteur de changement de pas (56) pour interagir avec ladite vanne de changement de pas (40) et bouleverser ledit équilibre hydraulique.
  13. Système de commande d'hélice (20) selon la revendication 12, dans lequel ladite vanne de changement de pas (40) comprend une vanne de signal de changement de pas (70) mobile par rapport à un tiroir de vanne de changement de pas (64), ladite vis de blocage de pas (52) étant opérationnelle pour bouleverser ledit équilibre hydraulique entre ladite vanne de signal de changement de pas (70) et ledit tiroir de vanne de changement de pas (64).
  14. Système de commande d'hélice (20) selon la revendication 1, comprenant en outre :
    un piston d'actionnement de changement de pas (48) entre une chambre d'actionneur de grand pas et une chambre d'actionneur de petit pas, ledit piston d'actionnement de changement de pas (48) étant mobile le long dudit premier axe (A) en réponse à une pression différentielle entre ladite chambre d'actionneur de grand pas et ladite chambre d'actionneur de petit pas, ledit piston d'actionnement de changement de pas (48) étant lié à la pluralité de pales d'hélice (32) pour en changer le pas ;
    où un mouvement de ladite vanne de changement de pas (40) est opérationnel pour communiquer sélectivement à chacune de ladite chambre d'actionneur de grand pas et ladite chambre d'actionneur de petit pas soit une pression d'alimentation, soit une pression de vidange ; et comprenant en outre
    un solénoïde de mise en drapeau (44) en communication avec ledit palier de transfert (38), un actionnement dudit solénoïde de mise en drapeau (44) est opérationnel pour augmenter ladite pression d'alimentation et bouleverser ledit équilibre hydraulique de telle sorte que ladite chambre d'actionneur de grand pas communique avec ladite pression d'alimentation et ladite chambre d'actionneur de petit pas communique ladite pression de vidange pour changer le pas de ladite pluralité de pales d'hélice (32) vers le grand pas.
  15. Système de commande d'hélice (20) selon la revendication 14, dans lequel ladite vanne de changement de pas (40) comprend un manchon de vanne de changement de pas (66), un tiroir de vanne de changement de pas (64), une vanne de signal de changement de pas (70), et une vanne d'actionnement de drapeau (68), ledit tiroir de vanne de changement de pas (64) étant mobile par rapport audit manchon de vanne de changement de pas (66) et à ladite vanne de signal de changement de pas (70), et ladite vanne d'actionnement de drapeau (68) étant mobile par rapport audit tiroir de vanne de changement de pas (64).
  16. Système de commande d'hélice (20) selon la revendication 15, dans lequel ladite pression d'alimentation est régulée en une première pression régulée au sein d'une chambre de signal de changement de pas (74) formée entre ladite vanne de signal de changement de pas (70) et ledit tiroir de vanne de changement de pas (64) et en une seconde pression régulée au sein d'une chambre de surpassement de drapeau (78) formée entre ladite vanne d'actionnement de drapeau (68) et ledit tiroir de vanne de changement de pas (64).
  17. Système de commande d'hélice (20) selon la revendication 15, comprenant en outre une vis de blocage de pas (52) adjacente à ladite vanne de signal de changement de pas (70), une rotation de ladite vis de blocage de pas (52) étant opérationnelle pour bouleverser une pression régulée au sein d'une chambre de signal de changement de pas (74) formée entre ladite vanne de signal de changement de pas (70) et ledit tiroir de vanne de changement de pas (64) et entraîner hydrauliquement ledit tiroir de vanne de changement de pas (64) par rapport audit manchon de vanne de changement de pas (66).
  18. Système de commande d'hélice (20) selon la revendication 14, dans lequel ledit palier de transfert (38) est monté autour dudit arbre d'hélice (28).
  19. Procédé de commande d'un pas de pale d'hélice comprenant les étapes suivantes:
    (1) fournir un fluide à une première pression d'alimentation à une vanne de changement de pas (40) pour maintenir la vanne de changement de pas (40) dans un équilibre hydraulique ;
    (2) bouleverser mécaniquement l'équilibre hydraulique de ladite vanne de changement de pas (40) pour déplacer axialement la vanne de changement de pas (40) et changer une première pression au sein d'une chambre d'actionneur de grand pas et une seconde pression au sein d'une chambre d'actionneur de petit pas ; et
    (3) déplacer axialement un piston d'actionnement de changement de pas (48) en réponse à ladite étape (2), ledit piston d'actionnement de changement de pas (48) étant lié à une pluralité de pales d'hélice (32) pour en changer le pas,
    caractérisé en ce que ledit bouleversement dudit équilibre hydraulique se fait par rotation d'une vis de blocage de pas (52) et d'un moteur de changement de pas (56).
  20. Procédé selon la revendication 19, comprenant en outre l'étape consistant à :
    fournir le fluide à une seconde pression d'alimentation plus grande que la première pression d'alimentation pour bouleverser l'équilibre hydraulique de la vanne de changement de pas (40) pour augmenter la première pression et diminuer la seconde pression de telle sorte que le pas de la pluralité de pales d'hélice (32) se déplace vers le grand pas.
  21. Procédé selon la revendication 19, comprenant en outre l'étape consistant à :
    auto-annuler le mouvement axial de la vanne de changement de pas (40).
  22. Procédé selon la revendication 19, comprenant en outre l'étape consistant à :
    faire communiquer sélectivement chacune de la première pression et de la seconde pression avec la première pression d'alimentation ou une pression de vidange en réponse à un mouvement axial de la vanne de changement de pas (40).
EP03716179A 2002-03-19 2003-02-25 Systeme d'actionnement pour une helice a pas reglable Expired - Lifetime EP1485288B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US102478 2002-03-19
US10/102,478 US6811376B2 (en) 2002-03-19 2002-03-19 Actuation system for a controllable pitch propeller
PCT/US2003/005770 WO2003080430A1 (fr) 2002-03-19 2003-02-25 Systeme d'actionnement pour une helice a pas reglable

Publications (2)

Publication Number Publication Date
EP1485288A1 EP1485288A1 (fr) 2004-12-15
EP1485288B1 true EP1485288B1 (fr) 2010-12-15

Family

ID=28040225

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03716179A Expired - Lifetime EP1485288B1 (fr) 2002-03-19 2003-02-25 Systeme d'actionnement pour une helice a pas reglable

Country Status (5)

Country Link
US (1) US6811376B2 (fr)
EP (1) EP1485288B1 (fr)
AU (1) AU2003219895A1 (fr)
DE (1) DE60335348D1 (fr)
WO (1) WO2003080430A1 (fr)

Families Citing this family (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7582092B2 (en) 2003-06-25 2009-09-01 Depuy Products, Inc. Assembly tool for modular implants and associated method
US8998919B2 (en) 2003-06-25 2015-04-07 DePuy Synthes Products, LLC Assembly tool for modular implants, kit and associated method
US7297166B2 (en) 2003-06-25 2007-11-20 Depuy Products, Inc. Assembly tool for modular implants and associated method
US8267656B2 (en) * 2006-03-08 2012-09-18 Hamilton Sundstrand Corporation Propeller pitch lock system
US8556912B2 (en) 2007-10-30 2013-10-15 DePuy Synthes Products, LLC Taper disengagement tool
US8518050B2 (en) 2007-10-31 2013-08-27 DePuy Synthes Products, LLC Modular taper assembly device
US8210798B2 (en) 2008-02-13 2012-07-03 United Technologies Corporation Cooled pusher propeller system
US8133027B2 (en) * 2008-07-14 2012-03-13 Hamilton Sundstrand Corporation Integrated actuator for a propeller system
US8439640B2 (en) * 2008-07-15 2013-05-14 Hamilton Sundstrand Corporation Propeller blade pitch control system
US8162611B2 (en) * 2008-07-15 2012-04-24 Hamilton Sundstrand Corporation Controllable pitch propeller with electrical power generation
US20100014977A1 (en) * 2008-07-15 2010-01-21 Shattuck Colman D Variable pitch aft propeller vane system
GB0821239D0 (en) * 2008-11-21 2008-12-31 Rolls Royce Plc A machine such as a gas turbine
US8172530B2 (en) * 2009-06-09 2012-05-08 Hamilton Sundstrand Corporation Pitch change actuation system for a counter-rotating propeller
US8167553B2 (en) * 2009-06-09 2012-05-01 Hamilton Sundstrand Corporation Electrical system for driving a propeller pitch change mechanism
US8277182B2 (en) * 2009-07-02 2012-10-02 Hamilton Sundstrand Corporation Remote pitch controller for a variable pitch propeller
US8529205B2 (en) * 2009-12-10 2013-09-10 Hamilton Sundstrand Corporation Passive cyclic pitch control
US20110158808A1 (en) 2009-12-29 2011-06-30 Hamilton Sundstrand Corporation Method for propeller blade root flow control by airflow through spinner
GB201000144D0 (en) * 2010-01-07 2010-02-24 Rolls Royce Plc Pitch Change Apparatus
US8496436B2 (en) * 2010-01-11 2013-07-30 Hamilton Sundstrand Corporation Torque compensation for propeller pitch change mechanism
US8533921B2 (en) 2010-06-15 2013-09-17 DePuy Synthes Products, LLC Spiral assembly tool
US8522522B2 (en) 2010-07-30 2013-09-03 Hamilton Sundstrand Corporation Fan embedded power generator
US9095452B2 (en) 2010-09-01 2015-08-04 DePuy Synthes Products, Inc. Disassembly tool
CN106974698B (zh) 2011-04-06 2019-12-17 德普伊新特斯产品有限责任公司 植入修正髋关节假体的器械组件
US20130061652A1 (en) * 2011-09-13 2013-03-14 Seattle Safety Llc Crash test method and apparatus including pitch simulation
US9120559B2 (en) 2012-04-18 2015-09-01 Hamilton Sundstrand Corporation Propeller blade pitch actuation system
US9528815B2 (en) 2013-02-08 2016-12-27 Hamilton Sundstrand Corporation Transformer based sensor arrangement
US9482595B2 (en) 2014-02-05 2016-11-01 Sikorsky Aircraft Corporation Rotor state sensor system
US9969488B2 (en) * 2014-05-01 2018-05-15 Sikorsky Aircraft Corporation Automatic propeller torque protection system
US9973058B2 (en) 2014-07-23 2018-05-15 Hamilton Sundstrand Corporation Propeller in-hub power generation and control
PL226826B1 (pl) 2015-09-03 2017-09-29 Gen Electric Układ sterowania skokiem dozespołu wirnika, silnik turbospalinowy isposób sterowania katem skoku wielu łopat smigła
PL226824B1 (pl) * 2015-09-07 2017-09-29 Gen Electric Układ isposób regulacji skoku smigła
PL226825B1 (pl) 2015-09-07 2017-09-29 Gen Electric Układ isposób regulacji skoku smigła
FR3046409B1 (fr) * 2016-01-05 2018-02-09 Safran Aircraft Engines Systeme de commande de l'orientation des pales de soufflante d'une turbomachine a pion de blocage de mise en drapeau
EP4442565A2 (fr) * 2016-04-29 2024-10-09 Ratier-Figeac SAS Systèmes d'actionnement hydraulique
US10683082B2 (en) * 2016-04-29 2020-06-16 Ratier-Figeac Sas Hydraulic actuation systems
US10864979B2 (en) * 2018-06-27 2020-12-15 Pratt & Whitney Canada Corp. System and method for propeller feedback ring position detection
US10899433B2 (en) * 2018-07-10 2021-01-26 Pratt & Whitney Canada Corp. System and method for feathering an aircraft propeller
US10864980B2 (en) * 2018-07-10 2020-12-15 Pratt & Whitney Canada Corp. System and method for feathering an aircraft propeller
US11364990B2 (en) * 2018-08-06 2022-06-21 Pratt & Whitney Canada Corp. Variable pitch propeller control system
CN109606648B (zh) * 2018-12-12 2024-06-18 惠阳航空螺旋桨有限责任公司 一种飞机螺旋桨变距机构
CN109606647B (zh) * 2018-12-12 2024-06-18 惠阳航空螺旋桨有限责任公司 一种螺旋桨变距机构
US20200324877A1 (en) * 2019-04-09 2020-10-15 Pratt & Whitney Canada Corp. Method and system for feathering a propeller
DE102020132002A1 (de) 2020-12-02 2022-06-02 Rolls-Royce Deutschland Ltd & Co Kg Stellvorrichtung
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
FR3141443A1 (fr) * 2022-10-28 2024-05-03 Safran Aircraft Engines Mécanisme de changement de pas avec vérin de commande et dispositif de verrouillage de pas hors des chambres du vérin
FR3141441A1 (fr) * 2022-10-28 2024-05-03 Safran Aircraft Engines Mécanisme de changement de pas à cinématique inversée
IT202200022992A1 (it) 2022-11-08 2024-05-08 Ge Avio S R L Elica a passo variabile di un motore a turbina a gas

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934154A (en) * 1956-12-18 1960-04-26 Rotol Ltd Hydraulic variable pitch propellers
US2995190A (en) 1958-12-04 1961-08-08 Rotol Ltd Impellers
US3439745A (en) * 1966-03-30 1969-04-22 United Aircraft Corp Combined propeller pitch lock and low pitch stop system
US4645420A (en) * 1985-06-07 1987-02-24 Avco Corporation Propeller control system
US4756667A (en) 1987-07-06 1988-07-12 United Technologies Corporation Pitch control capacitance coupling
US4907992A (en) * 1988-10-17 1990-03-13 Bird-Johnson Company Oil distribution box for a marine controllable pitch propeller
US4893989A (en) * 1989-03-07 1990-01-16 United Technologies Corporation Variable propeller system incorporating a forward transfer bearing
US5037271A (en) 1989-12-26 1991-08-06 United Technologies Corporation Pitch control system
US5897293A (en) 1996-11-22 1999-04-27 United Technologies Corporation Counterweighted propeller control system
US6059528A (en) 1996-11-22 2000-05-09 United Technologies Corporation Electronic propeller control system
US6085870A (en) 1998-03-13 2000-07-11 Heidelberger Druckmaschinen Ag Lubricant transfer connection
US6077040A (en) 1998-05-01 2000-06-20 United Technologies Corporation Control system for blades for a variable pitch propeller
US6149166A (en) 1998-07-24 2000-11-21 Trw Inc. Apparatus for use in a vehicle suspension
US6261062B1 (en) 2000-01-17 2001-07-17 Brunswick Corporation Actuation system for a controllable pitch propeller
US6422816B1 (en) 2001-05-21 2002-07-23 Hamilton Sundstrand Corporation Variable pitch propeller control system

Also Published As

Publication number Publication date
DE60335348D1 (fr) 2011-01-27
WO2003080430A1 (fr) 2003-10-02
AU2003219895A1 (en) 2003-10-08
US20030180146A1 (en) 2003-09-25
US6811376B2 (en) 2004-11-02
EP1485288A1 (fr) 2004-12-15

Similar Documents

Publication Publication Date Title
EP1485288B1 (fr) Systeme d'actionnement pour une helice a pas reglable
EP1832509B1 (fr) Système d'actionnement à verrouillage tonal à propulsion contrôlée
EP3712058B1 (fr) Soupape de commande combinée de survitesse, de mise en drapeau et de déclenchement inverse pour un ensemble d'hélice
US11873771B2 (en) Propeller assembly and pitch control unit
US5836743A (en) Variable pitch counterweighted propeller system with releasable hydraulic pitchlock
EP0598067B1 (fr) Systeme de commande de changement de pas des pales
US5186608A (en) Hydraulic low pitch switch for propeller pitch change system
EP0506891B1 (fr) Systeme de reglage du pas d'helice
EP1832510B1 (fr) Système de blocage du pas d'une hélice
US6981844B2 (en) Cyclic actuation system for a controllable pitch propeller and a method of providing aircraft control therewith
CA2105339C (fr) Systeme de commande d'une helice a pas variable, a pleine autorite
JPH0364713B2 (fr)
EP1270408B1 (fr) Système régulateur de vitesse de secours pour une hélice à pas variable
US5391055A (en) Propeller pitch change mechanism with impulse turbines
US20220266982A1 (en) Blade pitch control
EP4442565A2 (fr) Systèmes d'actionnement hydraulique
WO2004044436A1 (fr) Actionneur electro-hydraulique a retour de position d'asservissement mecanique
CN117396678A (zh) 用于具有顺桨位置的涡轮发动机螺旋桨的电液桨距控制系统
WO2000037797A1 (fr) Turbine a air dotee d'un systeme de commande fixe de decrochage

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20040915

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO

17Q First examination report despatched

Effective date: 20080707

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 60335348

Country of ref document: DE

Date of ref document: 20110127

Kind code of ref document: P

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20110916

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 60335348

Country of ref document: DE

Effective date: 20110916

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20130220

Year of fee payment: 11

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60335348

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 60335348

Country of ref document: DE

Effective date: 20140902

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140902

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20200123

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20200122

Year of fee payment: 18

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210225

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210225

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210228